Abstract
Language | English |
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Pages | Paper IAC-13-C1.6.7 |
Number of pages | 11 |
Publication status | Published - 23 Sep 2013 |
Event | 64th International Astronautical Congress 2013 - Beijing, China Duration: 23 Sep 2013 → 27 Sep 2013 |
Conference
Conference | 64th International Astronautical Congress 2013 |
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Country | China |
City | Beijing |
Period | 23/09/13 → 27/09/13 |
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Keywords
- Hohmann Spiral Transfer (HST)
- high-thrust propulsion
- low-thrust propulsion
- geostationary earth orbit
Cite this
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Novel numerical optimisation of the Hohmann Spiral Transfer. / Owens, Steven Robert; Macdonald, Malcolm.
2013. Paper IAC-13-C1.6.7 Paper presented at 64th International Astronautical Congress 2013, Beijing, China.Research output: Contribution to conference › Paper
TY - CONF
T1 - Novel numerical optimisation of the Hohmann Spiral Transfer
AU - Owens, Steven Robert
AU - Macdonald, Malcolm
N1 - COPYRIGHT OWNED BY AUTHOR STEVEN ROBERT OWENS
PY - 2013/9/23
Y1 - 2013/9/23
N2 - As the revenue of commercial spacecraft platforms is generated by its payload, of which the capacity is maximised when fuel-mass is minimised, there is great interest in ensuring the fuel required for the trajectory to deliver the satellite to its working orbit is minimum. This paper presents an optimisation study of a novel orbit transfer, recently introduced by the authors through an analytical analysis, known as the Hohmann Spiral Transfer . The transfer is analogous to the bi-elliptic transfer but incorporating high and low-thrust propulsion. This paper has shown that substantial fuel mass savings are possible when utilizing the HST. For a transfer to Geostationary Earth Orbit it is shown that a fuel mass saving of approximately 320 kg (~ 5 - 10% of mwet ) is possible for a wet mass of 3000-6000 kg – whilst satisfying a time constraint of 90 days. Several trends in the gathered data are also identified that determine when the HST with high or low-thrust plane change should be used to offer the greatest fuel mass benefit.
AB - As the revenue of commercial spacecraft platforms is generated by its payload, of which the capacity is maximised when fuel-mass is minimised, there is great interest in ensuring the fuel required for the trajectory to deliver the satellite to its working orbit is minimum. This paper presents an optimisation study of a novel orbit transfer, recently introduced by the authors through an analytical analysis, known as the Hohmann Spiral Transfer . The transfer is analogous to the bi-elliptic transfer but incorporating high and low-thrust propulsion. This paper has shown that substantial fuel mass savings are possible when utilizing the HST. For a transfer to Geostationary Earth Orbit it is shown that a fuel mass saving of approximately 320 kg (~ 5 - 10% of mwet ) is possible for a wet mass of 3000-6000 kg – whilst satisfying a time constraint of 90 days. Several trends in the gathered data are also identified that determine when the HST with high or low-thrust plane change should be used to offer the greatest fuel mass benefit.
KW - Hohmann Spiral Transfer (HST)
KW - high-thrust propulsion
KW - low-thrust propulsion
KW - geostationary earth orbit
UR - http://www.iac2013.org/dct/page/1
M3 - Paper
SP - Paper IAC-13-C1.6.7
ER -